Rotary wing aircraft with two engines and lateral engine fixations

A rotary wing aircraft, with a fuselage that forms an aircraft interior region, the fuselage comprising an upper primary skin that separates the aircraft interior region from an aircraft upper deck arranged above the fuselage, the upper primary skin being mounted on top of a predetermined number of supporting beams;

• wherein the aircraft upper deck comprises a first engine compartment arranged at a starboard side of the rotary wing aircraft, a second engine compartment arranged at a port side of the rotary wing aircraft, a tail rotor drive shaft that is arranged between the first and second engine compartments, a first firewall that separates the tail rotor drive shaft from the first and second engine compartments, a second firewall that separates the first and second engine compartments from each other, a third firewall that separates the first and second engine compartments from the upper primary skin, and a central bracket rigidly attached to the upper primary skin below the tail rotor drive shaft and providing a first central bracket lug in the first engine compartment above the third firewall and a second central bracket lug in the second engine compartment above the third firewall, the first, second, and third firewalls defining fire proof separations between the first and second engine compartments and the tail rotor drive shaft, between the first and second engine compartments, and between the first and second engine compartments and the upper primary skin, respectively, wherein the first engine compartment comprises a first rear mount, a first outboard fixation, and a first inboard fixation that are adapted for receiving a first aircraft engine, and wherein the second engine compartment comprises a second rear mount, a second outboard fixation, and a second inboard fixation that are adapted for receiving a second aircraft engine, wherein the first inboard fixation comprises a first inner main mounting bracket adapted for being rigidly attached to the first aircraft engine, a first inboard main mount that attaches the first inner main mounting bracket with a first beam web of at least one first beam of the predetermined number of supporting beams, and a first inboard lateral mount that attaches the first inner main mounting bracket with the first central bracket lug, and wherein the second inboard fixation comprises a second inner main mounting bracket adapted for being rigidly attached to the second aircraft engine, a second inboard main mount that attaches the second inner main mounting bracket with a second beam web of at least one second beam of the predetermined number of supporting beams, and a second inboard lateral mount that attaches the second inner main mounting bracket with the second central bracket lug.